Pneumatic gliding wing for a freefall jumper

ABSTRACT

The invention relates to a pneumatic gliding wing ( 1 ) for a freefall jumper ( 2 ), comprising a rigid part ( 3 ) which is made of, for example, a composite material such as GFK or CFK. Said rigid part is provided with a recess ( 5 ) for a parachute ( 6 ) for the jumper ( 2 ) and contains a device for supplying and administering compressed gas. Said rigid part has a pocket ( 7 ) with a closure ( 8 ) and eyelets ( 9 ) for the parachute of the pneumatic gliding wing ( 1 ) which is arranged on the side orientated towards the jumper ( 2 ). A cord ( 10 ) is drawn through the eyelets ( 9 ) and can, for example, be secured to a leg of the jumper ( 2 ). Outer parts ( 4 ) which can be impinged upon with pressurised gas are secured to the outer rigid part ( 3 ) of the pneumatic gliding wing ( 1 ) and are activated only when the jumper has left the aeroplane. When the gliding phase has finished, the jumper opens the parachute ( 6 ) and so long as this is done, the jumper opens a discharge valve on the outer parts ( 4 ) which fold back, whereupon the jumper can land in the normal way with the parachute ( 6 ).

The present invention is concerned with a pneumatic gliding wing forfreefall jumpers according to the precharacterizing clause of patentclaim 1.

A particular type of parachuting sport is known in which theparachutists first of all allow themselves to fall in freefall forseveral hundred to several thousand meters and the parachutes open onlyfor the last phase of the jump. In this freefall phase, the jumper canbe steered to a limited extent; however, actual flying cannot occur foraerodynamic reasons.

This has led to some freefall jumpers of this type buckling on shortwings which, to a limited extent, permit flying, flying which can becontrolled by the body directly, without the assistance of controlelements. Due to the size of the exit doors of the aircraft used by thefreefall jumpers, narrow limits are placed on the wings which can beused, and so a lift/drag ratio in the range of 2 to 3 approximatelyrepresents the prior art.

Even if the exit hatch of the aircraft used permits the use of a winghaving a large span, the fact remains, as a substantial drawback, thatthe wing has to jettisoned in the landing phase: if the jumper opens theparachute, then the wing, on which the flow impinges transversely in theposition of the jumper which is now necessary, produces such an airresistance that the parachute cannot be brought into the correctposition. For this reason, the known gliding wings are not onlyconstructed virtually without exception in a manner such that they canbe jettisoned—which is necessary for safety reasons—but also actuallyhave to be jettisoned. These wings are therefore always equipped withtheir own parachute. After landing with the parachute, the freefalljumper therefore also has to rescue his wing.

A gliding wing which is not provided pneumatically is disclosed, forexample, in DE 197 49 936 (D). This wing overcomes the abovementioneddrawback of the limited size of the exit doors by the fact that it haswing parts which can be unfolded and folded. These are intended to beunfolded either after the jump from the aircraft by the muscle power ofthe jumper or by the action of actuators which are tensioned before thejump, in any case, therefore, purely mechanically. For the landing ofthe jumper provision is made—as mentioned—to separate the wing from thejumper, so that the landing using the parachute can take place in anaerodynamically undisturbed manner.

U.S. Pat. No. 3,372,893 (D2) has disclosed a pneumatic gliding wingwhich is closer to the present invention. D2 proposes integrating agliding wing in the ejection seat of a fighter pilot who, after makingan emergency exit and suspended from the parachute, can activate thegliding wing using compressed gas. The intention is then for it to bepossible for the parachute to be jettisoned.

The wing proposed here in D2 does not fulfill essential requirementswhich are made of a wing. In addition, such considerable quantities ofgas are required in order to inflate an entire gliding aircraft asclaimed here that they are not suitable as a working load for a fighterpilot in an emergency exit.

A pneumatic wing per se is furthermore disclosed in EP 0 851 829 (D3) bythe same applicant as for the above patent application.

The object of the present invention is to provide a pneumatic glidingwing for freefall jumpers which improves the lift/drag ratio, isreliable in operation and can be worn right up to landing.

The achievement of the object which is set is reproduced in thecharacterizing part of patent claim 1 in respect of its essentialfeatures, and in the following claims in respect of further advantageousdevelopments.

The invention is explained in greater detail with reference to theattached drawing, in which

FIG. 1 shows a first exemplary embodiment of a pneumatic gliding wingaccording to the invention in a plan view,

FIG. 2 shows the first exemplary embodiment in the inoperative state inthe view from the front,

FIG. 3 shows a cross section through the pneumatic part of the pneumaticgliding wing,

FIG. 4 shows an exert of the longitudinal section of the pneumaticgliding wing,

FIG. 5 shows a detail of the connection of the pneumatic part of thepneumatic gliding wing in one perspective,

FIG. 6 shows the illustration of FIG. 4 in a longitudinal sectionrunning perpendicularly thereto,

FIG. 7 shows a device for supplying and managing the compressed gas,

FIG. 8 shows a second exemplary embodiment in the illustration of FIG.2.

FIG. 1 is the illustration of a first exemplary embodiment of apneumatic gliding wing 1 in the plan view from above, together with ajumper 2. The pneumatic gliding wing 1 is divided into a central, fixedpart 3 and two outer parts 4 which are attached thereto and are designedas pneumatic wings, for example in accordance with EP 0 851 829. Thesewings have a slack state and an operative state in which they arecharged with compressed gas. FIG. 1 illustrates the operative state.

The jumper 2 wears the fixed part 3 of the pneumatic gliding wingbuckled onto the rear side of his body by straps (not visible here). Thefixed part 3 has a relatively large cutout 5 which leaves space for afolded parachute 6 which is stowed in the corresponding bag. A furtherbag 7 is fitted, for example, in the lower part of the fixed part 3 andcontains the parachute for the pneumatic gliding wing 1 (illustrated bydashed lines in FIG. 1, since it is situated on that side of the wing 1which faces the jumper 2). This bag 3 has a fastening 8 with, forexample, three eyelets 9 through which a plastic chord 10 is pulled, theother end of which is fastened, for example, to a leg of the jumper 2.If he has to be separated from his pneumatic gliding wing 1, which isonly envisaged for emergency situations, then the spatial separation ofpneumatic gliding wing 1 and jumper 2 causes the chord 10 to be pulledout of the eyelets 9, the fastening 8 of the bag 7 to open and dischargethe parachute folded up in it.

Of course, the bag 7 may also be integrated in the aerodynamicallyfavorably configured fixed part 3 of the pneumatic gliding wing 1 insuch a manner that the fastening 8 of the bag 7 has the same structureand surface quality as the fixed part 3. The design of the fastening 8is not affected by this.

FIG. 2 illustrates the pneumatic gliding wing 1 from FIG. 1 in anuninflated state in the view from the front; the illustration of thejumper 2 has been omitted here. The outer parts 4 are, as illustrated,bent back by the flow, which is illustrated in FIG. 2 by an arrow.Before the jump out of the carrier aircraft and before the inflation ofthe outer parts 4, the latter can be held back on the fixed parts 3 ofthe pneumatic gliding wing 1 by a tape 11. The tape 11 acts on the tipof the outer part 4 (as on the left in FIG. 2) or in the vicinitythereof (as on the right in FIG. 2), and is set back in such a mannerthat small forces in the range of 1-5 N cause it either to tear orbecome completely detached from the pneumatic gliding wing 1.

Whereas the fixed part 3 of the pneumatic gliding wing 1 is designed ina manner known per se from composite materials, such as glassfiber-reinforced plastic or carbon fiber-reinforced plastic, the outerparts 4, as already mentioned, are designed as pneumatic wings. FIG. 3shows a cross section through one of the outer parts 4. Textile webs 14,as are disclosed, for example, in EP 0 851 829, are tensioned between anupper skin 12 and a lower skin 13 of a hermetically sealed envelope. Thetrailing edge (designated by the number 15) is tensioned by amultiplicity of approximately triangular supporting profiles 16 whichare essentially cut to the contour of a last pneumatic segment 17 andare supported thereon. The fixing of the supporting profiles on thesegment 17 and on the lower and upper skins 13, 12 is undertaken, forexample, by means of adhesive fastenings.

The transition from the fixed part 3 to the pneumatic outer parts 4 isillustrated in FIG. 4, a longitudinal section through the pneumaticgliding wing 1 transversely to the flying direction. A suitably shapedmetallic frame 18—illustrated on its own in FIGS. 5 a, b—is fastened tothe fixed part 3. The frame bears, for example, a shell-shaped structure19 in which an inflow opening 20 of a compressed-gas line 21 isarranged. The outer border of the frame 18 corresponds in shape and sizeprecisely to the inner border of the outer part 4, which is manufacturedfrom textile material. The webs 14 leave the upper and lower skins 12,13 of the outer part free to an extent sufficient to enable them to bepulled over the frame 18 and bonded and to fit snugly there. A secondframe 22 which corresponds in shape and size to the outer border of theouter part 4 at this point is slipped onto this frame. In order tosecure the outer frame 22, screws 23, for example, can be provided.

FIGS. 5 a, b are perspective illustrations of the frames 18, 22 forconnecting the fixed part 3 and one of the outer parts 4. Of course,there is a symmetrically designed pair of frames 18, 22 on the otherside of the fixed part 3. As FIGS. 5 a, b show, the outer contour of theinner frame 18 takes on, in the state in which it is charged withcompressed gas, the shape of the outer part 4 defined by the upper andlower skins 12, 13 and the textile webs 14. The same applies to theouter frame 22.

The inner frame 18 furthermore has a connecting web 24 whose functionnot only resides in the stabilization of the frame 18, but which serves,for example, as a diffuser for the compressed gas, as FIG. 6 shows.

FIG. 6 is a longitudinal section in the plane of the wing through anexert of the pneumatic gliding wing 1 in the region where the fixed part3 and the outer part 4 are joined together. The longitudinal sectionruns through the inflow opening 20 of the compressed-gas line 21. Thetextile webs 14 and the connecting web 24 are likewise cut away. Thecompressed gas flowing in through the inflow opening 20 impacts directlyagainst the connecting web 24 which has two roof-shaped bevels 26 in theregion of the axis (designated by 25) of the compressed-gas line 21 andthus distributes the flow of compressed gas. The compressed gas istherefore distributed rapidly to the individual segments of thepneumatic outer part 4 which lie between the webs 14. FIG. 7 is theillustration of a solution according to the invention of the supply andmanagement of compressed gas. There are two compressed-gas stores 30, 31which are arranged, for example, in the region of the wing centersections of the fixed part 3. The two stores have a volume of the orderof magnitude of 0.2 to 2 liters. The initial pressure in thecompressed-gas store 30 is dimensioned in such a manner that its fillingin accordance with the Boyle-Marriott lawp₁V₁=p₂V_(2 isothermal)where

-   -   p₁=pressure in the compressed-gas store 30    -   p₂=pressure in the outer parts 4, 40    -   V₁=volume of the compressed-gas store 30    -   V₂=volume of the outer parts 4, 40        is sufficient in order to pump the two outer parts 4 up to a        working pressure of the magnitude of approximately 400-600 hPa.        The compressed-gas store 30 is closed and opened by an        open-closed valve 32 which feeds the two compressed-gas lines 21        in a symmetrical arrangement.

The second compressed-gas store 31 with a volume V₃₁ of the same orderof magnitude of volume as V₁ has, for example, the maximum initialpressure, thus, for example, 200 bar. This pressure is used to act upona pressure-reducing valve 33 which reduces the pressure to, for example,5-10 bar. A second open-closed valve 34 operates at this pressure, theinitial pressure of the valve being brought by an adjustable controlvalve 35 to a working pressure of 400-600 hPa. This gas flow isdistributed in turn in a symmetrical arrangement through twocompressed-gas lines 36 to the two outer parts 4.

As an alternative to this, the compressed-gas lines 36 can lead into thecompressed-gas lines 21, or the gas flow of the control valve 35 can beguided directly into the compressed-gas line 21.

Furthermore, there is a connecting line 37 of large cross section whichconnects the two outer parts 4 and ensures that their pressure iscontinuously equalized. A pressure control valve 38 is fitted on theconnecting line 37 and—in a preadjustable manner—maintains thedesignated positive working pressure p₂, for example of 500 hPa, andreleases air flowing in through the control valve 35 if a positivepressure occurs.

If the jumper opens the wing at, for example, 5000 m above sea level,then the atmospheric pressure is approximately 550 hPa. If the jumperthen drops to approximately 500 m above sea level, the atmosphericpressure increases to approximately 950 hPa, which, in order to maintainthe mechanical properties of the pneumatic outer parts 4, 40,necessitates a continual redelivery of compressed gas from thecompressed-gas store 31. The presence of the pressure control valve 38makes it possible to always keep the internal pressure of the outerparts at a safe level. The actuation of the open-closed valves 32, 34takes place during flight. Their actuating members are therefore guidedonto the outside of the fixed part 3 and are arranged locally in such amanner that the jumper can open them with one maneuver in each case. Aclosing process during the flight is neither necessary nor envisaged.

When the jumper during the flight reaches the height at which he wouldlike to open his parachute 6, then he first of all actuates thetriggering mechanism thereof. As soon as the parachute 6 is supportinghim, he opens a relief valve, which is combined with the pressurecontrol valve 38, whereupon the air in the outer parts 4, 40 expands,and the latter fold to the rear. The air resistance of the pneumaticgliding wing 1, against which the flow now impinges transversely, istherefore reduced to such an extent that the jumper is able to undertakegliding using the parachute 6 with scarcely any impediment. Ajettisoning of the pneumatic gliding wing 1 is therefore not requiredduring normal operation of the pneumatic gliding wing 1. The possiblydifficult searching for and retrieval of the pneumatic gliding wing 1after the end of the parachuting phase is therefore also superfluous.

FIG. 8 illustrates a second exemplary embodiment of the pneumaticgliding wing 1 according to the invention. Like that of the firstexemplary embodiment according to FIGS. 1 and 2, it has a fixed part 3which is taken on without any changes. This fixed part 3 is adjoined bytwo short outer parts 40 which correspond in respect of construction andfastening to the outer parts 4 of the first exemplary embodiment. Wingtips 41 which are constructed in turn as fixed parts, similar to thefixed part 3, are fastened to these short outer parts 40. The connectionto the outer parts 40 takes place in the manner shown in FIGS. 4, 5.

Since it is neither necessary nor desired to charge the wing tips 41with compressed gas, these are hermetically sealed off from the outerparts 40 in the region of the inner frame 18. In the slack state, theouter parts 40 take on here a hinge function between the fixed part 3and the fixed wing tips 41. The initial pressure in the compressed-gasstore 30 can therefore be set to be lower; in addition, the period oftime between opening of the open-closed valve 32 and completeoperational readiness of the pneumatic gliding wing 1 is shortened.

1. A pneumatic gliding wing (1) for freefall jumpers (2), having aharness for fastening the pneumatic gliding wing (1) on the back of thejumper (2), having a separate parachute, which is folded in a bag (7),for the pneumatic gliding wing (1), and a cutout (5) for a parachute (6)which the jumper (2) wears on his back, characterized in that thepneumatic gliding wing (1) is constructed from a fixed part (3), whichcomprises and connects the wing center sections and to which the harnessis fastened, there are furthermore two outer parts (4, 40) which areattached in a hermetically sealed manner to the fixed part (3), whichouter parts (4, 40) consist of textile material, can be charged withcompressed gas and, in the operative state, are charged with compressedgas, which outer parts can furthermore be relieved of the compressed gasfor the inoperative state and can then fold away in the state in whichthe flow impinges transversely, so that the jumper can carry out theflight phase executed using the parachute (6) without jettisoning thepneumatic gliding wing (1), there is a device for the supply andmanagement of the compressed gas.
 2. The pneumatic gliding wing (1) asclaimed in patent claim 1, characterized in that the outer parts (4)consist of a textile upper skin (12) and a textile lower skin (13) whichare both connected by a multiplicity of textile webs (14) which aresituated essentially perpendicularly on the upper and lower skins (12,13) and with respect to the flow direction of the air around thepneumatic gliding wing (1), the upper and lower skins (12, 13)hermetically sealing the interior of each outer part (4) to the outside,but, the textile webs (14) being air-permeable and dividing the interiorof the outer parts (4) into a multiplicity of segments, a segment (17)which is rearmost in the flow direction being likewise sealedhermetically to the outside, the pneumatic gliding wing (1) having aleading edge (15) which is constructed and supported by a furthermultiplicity of supporting profiles (16), the supporting profiles (16)for their part being supported on the rearmost segment (17) of the outerparts (4), and the upper and lower skins (12, 13) extending over thesupporting profiles, being joined together behind them and beingtensioned by them, the textile materials for the upper and lower skins(12, 13) and for the folded webs (14) have little extensibility, theouter parts extend as far as the tips of the pneumatic gliding wing (1).3. The pneumatic gliding wing (1) as claimed in patent claim 2,characterized in that the fixed part (3) is hermetically sealed at itsends from the outer parts (4, 40) by a respective shell-shaped structure(19) which curves inward toward the fixed part (3) and which bears,essentially in the center, an inflow opening (20) of a compressed-gasline (21) which is directed toward the outer parts (4, 40), the fixedpart (3), at its outer ends toward the outer parts (4, 40), bears arespective first frame (18) which is connected fixedly to the fixed part(3) and the outer border of which corresponds in shape and sizeprecisely to the inner border of the outer parts (4, 40) which aremanufactured from textile material, the textile webs (14) leaving theupper and lower skins (12, 13) free sufficiently for them to be able tobe pulled over the frame (18) and to fit snuggly there, the upper andlower skins (12, 13) are bonded in a hermetically sealed manner to theframe (18) formed in this manner, there is a second frame (22) whichcorresponds in shape and size to the outer border of the outer part (4,40), and the second frame (22) can be pushed over the outer part (4,40), which is bonded to the frame (18), and can be secured there.
 4. Thepneumatic gliding wing (1) as claimed in patent claim 3, characterizedin that the first frame (18) has a connecting web (24) which runsessentially perpendicularly to the plane of the wing and is fittedlocally in such a manner that it lies on the longitudinal axis of theinflow opening (20) of the compressed-gas line (21) and is beveled in aroof-shaped manner on the side facing the latter.
 5. The pneumaticgliding wing (1) as claimed in patent claim 1, characterized in that theouter parts (40) consist of a textile upper skin (12) and a textilelower skin (13) which are both connected by a multiplicity of textilewebs (14) which are situated essentially perpendicularly on the upperand lower skins (12, 13) and with respect to the flow direction of theair around the pneumatic gliding wing (1), the upper and lower skins(12, 13) hermetically sealing the interior of each outer part (4) to theoutside, but, the textile webs (14) being air-permeable and dividing theinterior of the outer parts (4) into a multiplicity of segments, asegment (17) which is rearmost in the flow direction being likewisesealed hermetically to the outside, the pneumatic gliding wing (1)having a leading edge (15) which is constructed and supported by afurther multiplicity of supporting profiles (16), the supportingprofiles (16) for their part being supported on the rearmost segment(17) of the outer parts (40), and the upper and lower skins (12, 13)extending over the supporting profiles, being joined together behindthem and being tensioned by them, the textile materials for the upperand lower skins (12, 13) and for the folded webs (14) have littleextensibility, wing tips (41) adjoin the outer parts (40) on the outsideand are produced in a fixed construction and are hermetically sealedfrom the outer parts (40), the wing tips (41) are connected to the outerparts (40) in the same manner as the fixed part (3) is connected to theouter parts (40).
 6. The pneumatic gliding wing (1) as claimed in patentclaim 1, characterized in that there is a device for the supply andmanagement of compressed gas and it is accommodated in the fixed part(3) of the pneumatic gliding wing (1).
 7. The pneumatic gliding wing (1)as claimed in patent claim 6, characterized in that the device for thesupply and management of compressed gas has two compressed-gas stores(30, 31), the first compressed-gas store (30) with a volume V₁ beingfilled to the pressure p₁ sufficiently for the compressed gas stored init to reach when it expands into the volume V₂ of the outer parts (4,40) in order to produce the pressure p₂ there, in which casep₁V₁=p₂V_(2 isothermal) the second compressed-gas store (31) with avolume V₃₁ is filled to a pressure p₃₁ to an extent so that its contentsuffices in order to continuously maintain the positive pressure p₂ inthe outer parts (4, 40) during the dropping of the pneumatic glidingwing (1).
 8. The pneumatic gliding wing (1) as claimed in patent claim7, characterized in that the positive pressure P2 lies in the range from400-600 hPa.
 9. The pneumatic gliding wing (1) as claimed in patentclaim 7, characterized in that the first compressed-gas store (30) has afirst open-closed valve (32) which feeds the two compressed-gas lines(21) in a symmetrical arrangement, the second compressed-gas store (32)acts upon a pressure-reducing valve (33) which reduces the fillingpressure of the compressed-gas store (32) to a pressure of 5-10 bar,there is a second open-closed valve (34) which is arranged behind thepressure-reducing valve (33), there is a control valve (35) and it isarranged downstream of the second open-closed valve (34) and can be setin such a manner that it can maintain the positive pressure P2 providedin the outer parts (4), the control valve (35) outputs the compressedgas output by it in a symmetrical arrangement through two secondcompressed-gas lines (36) to the two outer parts (4).
 10. The pneumaticgliding wing (1) as claimed in patent claim 9, characterized in that thesecond compressed-gas lines (36) lead into the first compressed-gaslines (21).
 11. The pneumatic gliding wing (1) as claimed in patentclaim 9, characterized in that there is a connecting line (37) whichconnects the two outer parts (4, 40) and ensures a continuousequalization of pressure between these outer parts (4, 40).
 12. Thepneumatic gliding wing (1) as claimed in patent claim 11, characterizedin that a pressure control valve (38) is arranged on the connecting line(37) and can be set in such a manner that it lets out compressed gas ifthe positive pressure p₂ of the two outer parts (4, 40) exceeds thedesignated value.
 13. The pneumatic gliding wing (1) as claimed inpatent claim 12, characterized in that a relief valve is combined withthe pressure control valve (38), the relief valve making it possible torelieve the outer parts (4, 40), so that their internal pressurecorresponds permanently to the local atmospheric pressure.
 14. Thepneumatic gliding wing (1) as claimed in patent claim 13, characterizedin that there are actuating elements for the open-closed valves (32, 34)and the relief valve and they are arranged on the outside of thepneumatic gliding wing (1) in such a manner that they can be operatedduring the flight.